JP6314049B2 - Stationary member of rotating machine and gas turbine - Google Patents

Description

  The present invention relates to a stationary member of a rotary machine and a gas turbine.

  A gas turbine is composed of a compressor, a combustor, and a turbine. The compressed air is compressed into high-temperature and high-pressure compressed air, and the combustor supplies fuel to the compressed air. The turbine is driven by high-temperature and high-pressure combustion gas (exhaust gas) generated by this combustion, and a generator connected on the same axis can be driven to generate electric power.

  Here, in a rotary machine such as a gas turbine, stationary members such as stationary blades are annularly arranged. Such an annularly arranged member may be installed on a rotor that is a rotating part by dividing the annular portion into two parts, an upper half and a lower half (see Patent Document 1). Thus, when it is set as the structure which divided | segmented the cyclic | annular member by upper half, lower half, etc., a connection part is sealed and the air from a connection part is suppressing a leak. Moreover, also when dividing | segmenting into two or more, a connection part is sealed and the air from a connection part has suppressed leakage (refer patent document 2).

JP 2001-200705 A JP 2002-201913 A

  Here, the gas turbine includes a support ring that supports the stationary blade on the rotor side, and an intermediate shaft cover that is disposed on the radially inner side of the support ring and supports the support ring. This support ring is fixed to a predetermined position of the rotary machine by being supported by the intermediate shaft cover. In a rotating machine, an annular member such as a support ring or an intermediate shaft cover is basically divided into a half circumference and combined. However, a design restriction occurs only with the structure divided in half as described above. In addition, when the division position is changed, if the seal between the support ring and the intermediate shaft cover is insufficient, the performance of the rotating machine is degraded.

  An object of the present invention is to solve the above-described problems, and to provide a stationary member of a rotating machine and a gas turbine that can be designed with a higher degree of freedom and can increase efficiency during operation. To do.

  The present invention for achieving the above object is a stationary member of a rotary machine, wherein an outer peripheral ring in which a plurality of divided outer peripheral rings are connected to form an annular shape, and an inner peripheral ring inscribed in the outer peripheral ring In the outer ring, one of the partial outer rings is a main part outer ring, and a circumferential end of the main part outer ring or a circumferential direction of the main part outer ring of the inner ring A relief portion having a shape other than an arc is formed on at least one of the portions facing the end portion of the main portion so that a circumferential end portion of the main portion outer peripheral ring is larger in a radial direction than an outer peripheral surface of the inner peripheral ring. A portion that is formed on an end surface of the rotary machine in an axial direction of a portion where the relief portion is formed, and that faces an end portion of the main portion outer ring or an end portion of the main portion outer ring of the inner ring When viewed from at least one of the rotation axis directions of the rotary machine, Wherein the closing portion for closing the whole of the space between the inner ring and the main portion outer peripheral ring formed in-safe portion.

  Here, it is preferable that the main part outer peripheral ring is an arc larger than a half circumference.

  Moreover, it is preferable that the said relief part is formed in the said main part outer periphery ring | wheel, and is extended in the tangent direction of the circular arc from the edge part of the circular arc of a semicircle.

  Moreover, it is preferable that the said main part outer periphery ring is arrange | positioned in the part containing the edge part of the perpendicular direction upper side of the said outer periphery ring.

  Moreover, it is preferable that the said obstruction | occlusion part is formed in the said inner periphery ring, and contains the flange part which protruded in the said outer periphery ring side rather than the part in which the said relief part is formed.

  Moreover, it is preferable that the said obstruction | occlusion part is formed in the said main part outer periphery ring, and contains the flange part which protruded in the said inner periphery ring side rather than the part in which the said relief part is formed.

  The outer peripheral ring and the inner peripheral ring are formed on one of a circumferential end surface of the closing portion or a surface facing the circumferential end surface of the closing portion, and in a radial direction, a region overlapping the relief portion. It is preferable to have a seal plate that extends over the entire area and contacts the other of the circumferential end surface of the closing portion or the surface facing the circumferential end surface of the closing portion.

  Moreover, it is preferable that the said sealing board is arrange | positioned rather than the center of the axial direction of the said end surface at the space side formed in the said relief part.

  Moreover, it is preferable that the said sealing plate is formed in the surface facing the circumferential end surface of the said obstruction | occlusion part.

  To achieve the above object, the present invention provides a gas turbine, a compressor that compresses the taken-in air, a combustor that supplies and burns fuel to the compressed air compressed by the compressor, and the combustion A turbine that obtains rotational power by combustion gas combusted in a vessel, and the turbine includes a stationary member of the rotating machine according to any one of claims 1 to 7 and an outer periphery of the stationary member of the rotating machine. And a plurality of stationary blades supported on the outer periphery of the ring.

  The present invention provides a relief portion and a closing portion, so that even if one main part outer peripheral ring including the outer peripheral ring has a size of half or more, it can be installed on the inner peripheral ring, and the inner peripheral ring A seal between the ring and the outer ring can be maintained. Thereby, the position which divides | segments an annular member can be made into arbitrary positions other than the part used as a semicircle, and a sealing performance can also be maintained. Thereby, design can be performed with a higher degree of freedom, and the efficiency during operation can be increased.

FIG. 1 is a schematic diagram illustrating a gas turbine according to the present embodiment. FIG. 2 is a cross-sectional view showing a schematic configuration of the periphery of the first stage stationary blade and the moving blade of the gas turbine of FIG. FIG. 3 is a front view showing a schematic configuration of the stationary blade support mechanism. FIG. 4 is a front view showing the vicinity of the contact portion between the upper member and the lower member of the stationary blade support mechanism. FIG. 5 is a perspective view showing the vicinity of the end surface of the lower member of the stationary blade support mechanism. FIG. 6 is a top view showing the vicinity of the end face of the lower member of the stationary blade support mechanism. FIG. 7 is an enlarged top view showing the vicinity of the end face of the lower member of the stationary blade support mechanism. FIG. 8 is a perspective view showing a space between the intermediate bearing and the support ring. FIG. 9 is a partially enlarged view showing the vicinity of the contact portion between the upper member and the lower member of the stationary blade support mechanism. 10 is a cross-sectional view taken along line AA in FIG. FIG. 11 is a top view showing the vicinity of the end face of the lower member of the modified stationary blade support mechanism. FIG. 12 is a top view showing the vicinity of the end face of the lower member of the stationary blade support mechanism of another embodiment. FIG. 13: is a front view which shows the vicinity of the contact part of the upper member and lower member of the stationary blade support mechanism of another Example.

  Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In addition, this invention is not limited by this Example, Moreover, when there exists multiple Example, what comprises combining each Example is also included.

  FIG. 1 is a schematic diagram illustrating a gas turbine according to the present embodiment. As shown in FIG. 1, the gas turbine 10 includes a compressor 11, a combustor 12, and a turbine 13. A generator is connected to the gas turbine 10 so that power generation is possible.

  The compressor 11 has an air intake 21 for taking in air, and a plurality of compressor stationary blade bodies 23 and compressor moving blade bodies 24 are alternately arranged in a front-rear direction (an axial direction of a rotor 32 described later) in a compressor casing 22. The bleed chamber 25 is provided on the outside thereof. The combustor 12 is combustible by supplying fuel to the compressed air compressed by the compressor 11 and igniting it. In the turbine 13, a plurality of turbine stationary blade bodies 27 and turbine rotor blade bodies 28 are alternately arranged in a front-rear direction (an axial direction of a rotor 32 described later) in a turbine casing (casing) 26. An exhaust chamber 30 is disposed on the downstream side of the turbine casing 26 in the flow direction of the combustion gas via an exhaust casing 29, and the exhaust chamber 30 has an exhaust diffuser 31 continuous with the turbine 13. Yes.

  Further, a rotor (turbine shaft) 32 is disposed so as to penetrate the compressor 11, the combustor 12, the turbine 13, and the central portion of the exhaust chamber 30. The end of the rotor 32 on the compressor 11 side is rotatably supported by the bearing portion 33, while the end of the exhaust chamber 30 side is rotatably supported by the bearing portion 34. The rotor 32 is fixed by stacking a plurality of disks on which the compressor blade bodies 24 are mounted in the compressor 11, and a plurality of disks on which the turbine blade bodies 28 are mounted in the turbine 13. Overlaid and fixed.

  In this gas turbine, the compressor casing 22 of the compressor 11 is supported by the legs 35, the turbine casing 26 of the turbine 13 is supported by the legs 36, and the exhaust chamber 30 is supported by the legs 37. .

  The turbine casing 26 has a ring-shaped combustion gas passage 40 formed therein, and a plurality of turbine stationary blade bodies 27 and turbine rotor blade bodies 28 are arranged in the combustion gas passage 40 along the flow direction of the combustion gas. Are alternately arranged. That is, in each stage of the turbine stationary blade body 27, a plurality of turbine stationary blades (stator blades) 41 are arranged at equal intervals in the circumferential direction and fixed to the turbine casing 26.

  The air taken in from the air intake 21 of the compressor 11 passes through the plurality of compressor stationary blade bodies 23 and the compressor moving blade bodies 24 and is compressed to become high-temperature and high-pressure compressed air. A predetermined fuel is supplied to the compressed air in the combustor 12 and burned. The high-temperature and high-pressure combustion gas that is the working fluid generated by the combustor 12 passes through the plurality of turbine stationary blade bodies 27 and the turbine rotor blade bodies 28 that constitute the turbine 13 to drive and rotate the rotor 32. Then, the generator connected to the rotor 32 is driven. On the other hand, the energy of the exhaust gas (combustion gas) is converted into pressure by the exhaust diffuser 31 in the exhaust chamber 30 and decelerated before being released to the atmosphere.

  Next, the turbine stationary blade body 27 and the turbine rotor blade body 28 will be described with reference to FIG. 2 in addition to FIG. In the turbine 13, a plurality of turbine stationary blade bodies 27 (stator blades 41) and a plurality of turbine rotor blade bodies 28 (the blades 42) are alternately arranged, and after acquiring the energy of the combustion gas (exhaust gas). The exhaust gas can be discharged. Next, of the turbine stationary blade body 27 and the turbine rotor blade body 28, the first stage turbine stationary blade body 27 and the turbine rotor blade body 28, that is, the turbine stationary blade through which the combustion gas discharged from the combustor 12 first passes. The configuration of the blade body 27 and the turbine rotor blade body 28 will be described. In the following description, the first-stage turbine stationary blade body (first-stage stationary blade) 27 and the turbine rotor blade body (first-stage stationary blade) 28 will be described. However, the flow direction of the combustion gas is further downstream. The turbine rotor blade body 28 may have the same configuration or a different configuration.

  The turbine stationary blade body 27 includes a stationary blade 41, an outer shroud 43, and an inner shroud 44. In the turbine stationary blade body 27, an outer shroud 43 is fixed to one end portion (radially outer side) in the longitudinal direction (radial direction of the rotor 32) of the vane body of the stationary blade 41, and the other end portion (radial inner side). An inner shroud 44 is fixed. The outer shroud 43 is fixed to the turbine casing 26. The inner shroud 46 is fixed to a stationary blade support mechanism (stationary part of a rotating body) 50. Further, the stationary blade 41 has a hollow shape, and a plurality of cooling holes penetrating the inside and the outside are formed at predetermined positions. The turbine stationary blade body 27 is supplied with high-pressure cooled compressed air into the stationary blade 41 from the outer shroud 43 side and the inner shroud 44 side. The supplied cooled compressed air cools by colliding with the inner wall surface and then flows along the inner wall surface, and is discharged to the outside (combustion gas passage 40) through a number of cooling holes and flows along the outer wall surface. Cool with. The turbine blade body 28 includes a turbine blade (blade) 42 and a rotor disk 46. The turbine rotor blade bodies 28 are arranged at equal intervals in the circumferential direction. The turbine rotor blade body 28 is fixed to a rotor disk 46 in which a base end portion of the rotor blade 42 is fixed to the rotor 32. Thereby, the turbine rotor blade body 28 rotates integrally with the rotor 32.

  Next, the stationary blade support mechanism 50 will be described with reference to FIGS. 3 to 10 in addition to FIGS. 1 and 2. FIG. 4 is a front view showing the vicinity of the contact portion between the upper member and the lower member of the stationary blade support mechanism. FIG. 5 is a perspective view showing the vicinity of the end surface of the lower member of the stationary blade support mechanism. FIG. 6 is a top view showing the vicinity of the end face of the lower member of the stationary blade support mechanism. FIG. 7 is an enlarged top view showing the vicinity of the end face of the lower member of the stationary blade support mechanism. FIG. 8 is a perspective view showing a space between the intermediate bearing and the support ring. FIG. 9 is a partially enlarged view showing the vicinity of the contact portion between the upper member and the lower member of the stationary blade support mechanism. 10 is a cross-sectional view taken along line AA in FIG. 4 to 10 show only one of the divided surfaces, but the other has the same structure.

  As shown in FIGS. 2 and 3, the stationary blade support mechanism (rotating member stationary member) 50 includes an intermediate shaft cover 52, a support ring 54, and a fastening portion 56 that fastens the support ring to the intermediate shaft cover 52. And having. The intermediate shaft cover 52 has an inner peripheral surface facing the rotor 32. The intermediate shaft cover 52 is an annular member that is disposed around the rotor 32 and that has the rotation axis CL of the rotor 32 as an axis. The intermediate shaft cover 52 includes an intermediate shaft cover upper half 60 and an intermediate shaft cover lower half 62. The intermediate shaft cover upper half 60 and the intermediate shaft cover lower half 62 each have a semicircular shape obtained by cutting the ring in half, and connect the end of the intermediate shaft cover upper half 60 and the end of the intermediate shaft cover lower half 62. By doing so, it becomes one annular member. In the intermediate shaft cover 52, the intermediate shaft cover upper half 60 and the intermediate shaft cover lower half 62 have a semicircular shape. Therefore, the position of the contact portion between the intermediate shaft cover upper half 60 and the intermediate shaft cover lower half 62 is horizontal. 100. In the present embodiment, the horizontal plane 100 is used, but any plane that passes through the rotation axis CL may be used. In other words, a surface obtained by rotating the horizontal plane 100 by an arbitrary angle about the rotation axis CL may be the position of the contact portion between the intermediate shaft cover upper half 60 and the intermediate shaft cover lower half 62.

  The support ring 54 has an inner peripheral surface facing the intermediate shaft cover 52 and an outer peripheral surface facing the turbine stationary blade body 27. In FIG. 3, only one stationary blade 41 is shown, but the stationary blade 41 is arranged at a predetermined interval around the rotation axis CL as indicated by a black circle. The support ring 54 is fixed to the intermediate shaft cover 52 by a fastening portion 56, and the inner shroud 44 of the stationary blade 41 is fixed to the outer peripheral surface. The support ring 54 is disposed between the intermediate shaft cover 52 and the turbine stationary blade body 27 and connects the intermediate shaft cover 52 and the turbine stationary blade body 27. The support ring 54 is an annular member having the rotation axis CL as an axis, like the intermediate shaft cover 52. The support ring (outer peripheral ring) 54 includes a support ring upper half (main part outer peripheral ring) 64 and a support ring lower half 66. In the support ring 54, the support ring upper half 64 and the support ring lower half 66 have an arc shape with the rotation axis CL as the axis, and the ends of the support ring upper half 64 and the ring lower half 66 are connected to each other. It becomes two annular members. The support ring upper half 64 has an arc shape larger than the half circumference. The lower ring half 66 has an arc shape smaller than the half circumference. Since the support ring 54 has an arc in which the upper half 64 of the support ring is larger than the half circumference and the lower half 66 is smaller than the half circumference, the ends of the upper half 64 of the support ring and the lower half 66 of the support ring are connected. In this embodiment, the split surfaces 102 and 104, which are the surfaces where the end of the upper half 64 of the support ring and the end of the lower half 66 of the support ring contact, are displaced from the horizontal plane 100. This is the position where the lower half 62 is disposed.

  The fastening portion 56 is a bolt or the like, and is arranged at a predetermined interval in the circumferential direction around the rotation axis CL. The fastening portion 56 fastens the intermediate shaft cover 52 to the support ring 54. Here, the fastening portion 56 is disposed in a direction extending in the direction of the rotation axis CL, and presses the intermediate shaft cover 52 against the support ring 54 in the direction of the rotation axis CL. Further, the fastening portion 56 protrudes from the surface opposite to the surface facing the turbine rotor body 28.

  The stationary blade support mechanism 50 fastens the intermediate shaft cover 52 and the support ring 54 with the fastening portion 56, and supports the inner shroud 44 of the turbine stationary blade body 27 with the support ring 54. The body 27 is supported.

  Next, the shapes of the intermediate shaft cover (inner circumferential ring) 52 and the support ring (outer circumferential ring) 54 of the stationary blade support mechanism 50, particularly the horizontal plane 100 and the divided planes 102 and 104 where the upper half and the lower half face each other. The shape in the vicinity will be described.

  The support ring upper half 64 has an arc shape wider than the semicircle, and the end portion in the circumferential direction, specifically, the portion outside the semicircle (obtuse angle side) in the circumferential direction becomes the relief portion 70. The relief portion 70 extends to a position that faces the lower half 66 of the support ring in a direction that is a tangent to an arc at a position that is a semicircle in the circumferential direction. Since the support ring upper half 64 is provided with the relief portion 70, the end surface on the inner peripheral side of the portion outside the semicircle in the circumferential direction where the relief portion 70 is provided is the diameter of the inner peripheral surface of the semicircular portion. The same position as the outermost part of the direction. Thereby, the distance of the line which connected the edge part of the circumferential direction becomes the same magnitude | size as the diameter of the internal peripheral surface of a semicircle part. The support ring upper half 64 is provided with the relief portion 70 so that the inner peripheral end surface of the portion outside the semicircle in the circumferential direction where the relief portion 70 is provided has a diameter larger than the outer peripheral surface of the intermediate shaft cover 52. Get bigger in the direction. Since the support ring upper half 64 is provided with the relief portion 70, even when the support ring upper half 64 is installed on the intermediate shaft cover 52 from the vertical direction of the rotation axis CL, the end in the circumferential direction is attached to the intermediate shaft cover 52. It can suppress being caught.

  The intermediate shaft cover 52 has a flange portion 71 formed on the outer peripheral surfaces of the intermediate shaft cover upper half 60 and the intermediate shaft cover lower half 62, that is, at positions facing the support ring 54. The flange portion 71 has an intermediate shaft cover upper half 60 and an intermediate shaft on the upstream side in the flow direction of the combustion gas G in the direction of the rotation axis CL, specifically, on the opposite side to the surface facing the turbine rotor blade body 28. It is formed on the outer peripheral surface of the cover lower half 62 and protrudes radially outward from the other parts. The flange part 71 is formed in the whole area of the circumferential direction.

  Further, the support ring upper half 64 and the support ring lower half 66 are formed with a recess 73 that is recessed from the other portions at a position facing the flange portion 71. The concave portion 73 formed in the upper half 64 of the support ring is also formed at a position corresponding to the relief portion 70. The portion that is the flange portion 71 and the relief portion 70 protrudes radially outward from the radially inner end of the flange portion 72 described later of the relief portion 70, but is radially outward from the recessed portion 74 described later. It does not protrude.

  Next, the support ring upper half 64 and the support ring lower half 66 are formed with flange portions 72 at positions facing the inner peripheral surface, that is, the intermediate shaft cover. The flange portion 72 is formed on the support ring upper half 64 and the support ring lower half 66 on the downstream side in the flow direction of the combustion gas G in the direction of the rotation axis CL, specifically, on the surface side facing the turbine rotor blade body 28. It is formed on the inner peripheral surface and protrudes radially inward from the other parts. The flange part 72 is formed in the whole area of the circumferential direction. The flange portion 72 formed on the support ring upper half 64 is also formed at a position corresponding to the relief portion 70. The portion that is the flange portion 72 and the relief portion 70 protrudes radially inward from the flange portion 71 of the relief portion 70, but does not protrude radially inward from the recess 73.

  Further, the intermediate shaft cover 52 is formed with a recess 74 that is recessed from the other portions at a position facing the flange portion 72 of the intermediate shaft cover upper half 60 and the intermediate shaft cover lower half 62. As described above, the stationary blade support mechanism 50 has the flange portion 71 formed on the outer peripheral surface of the intermediate shaft cover 52 in the flow direction upstream of the combustion gas G, and the recess 74 formed on the downstream side in the flow direction of the combustion gas G. Yes. Further, as described above, in the stationary blade support mechanism 50, the concave portion 73 is formed on the inner peripheral surface of the support ring 54 on the upstream side in the flow direction of the combustion gas G, and the flange portion 72 is formed on the downstream side in the flow direction of the combustion gas G. Has been.

The stationary blade support mechanism 50 has flange portions 71 and 72 and concave portions 73 and 74 on the downstream side in the flow direction of the combustion gas G in the direction of the rotation axis CL, specifically, on the side facing the rotor blade body 24. And formed. Here, the protruding distance of the radial direction of the flange portions 71 and 72 and the recesses 73 and 74, indentation distance is the least distance for closing the space _{A 1} to be described later.

  Thereby, in the direction of the rotation axis CL of the flange portion 72 protruding inward in the radial direction of the support ring 54, the upstream surface (support ring side end surface) 77 in the flow direction of the combustion gas G rotates the intermediate shaft cover upper half 60. In the axis CL direction, the flange 71 (portion where the recess 74 is not formed) is in a state of facing and in contact with the rotation axis CL direction and the downstream surface (intermediate shaft cover side end face) 79 in the flow direction of the combustion gas G. Further, in the stationary blade support mechanism 50, the support ring side end surface 77 of the portion where the relief portion 70 is formed has a flange portion 71 (a portion where the concave portion 74 is not formed) in the rotation axis CL direction of the intermediate shaft cover lower half 62. ) Is also in a state of facing and in contact with the surface 79 on the downstream side in the flow direction of the combustion gas G (the intermediate shaft cover side end surface) 79. Further, in the direction of the rotation axis CL of the flange portion 72 protruding inward in the radial direction of the support ring 54, the upstream surface (support ring side end surface) 77 in the flow direction of the combustion gas G is the rotation axis of the intermediate shaft cover lower half 62. In the CL direction, the portion where the recess 74 is not formed is in a state of facing and in contact with the surface 79 on the downstream side in the flow direction of the combustion gas G (intermediate shaft cover side end surface) 79.

  Next, the lower half 66 of the support ring is arranged on the surface facing the upper half 64 of the support ring, that is, the end face in the circumferential direction, and the seal plate 82 extending in the radial direction and projecting to the upper half 64 of the support ring is disposed. . The seal plate 82 is provided in a portion where the flange portion 72 is formed in the rotation axis CL direction. Further, the seal plate 82 is disposed in the entire area facing the support ring upper half 64 in the radial direction, and the radially inner end portion is more radial than the radially outer end portion of the intermediate shaft cover side end surface 79. Inside. The end portion on the support ring upper half 64 side of the seal plate 82 is in contact with the support ring upper half 64 and seals between the support ring upper half 64 and the support ring lower half 66.

  Further, the lower half 62 of the intermediate shaft cover is provided with a seal plate 84 that extends in the radial direction and protrudes from the upper half 60 of the bearing on a surface facing the upper half 60 of the bearing, that is, an end surface in the circumferential direction. The seal plate 84 is provided at a position adjacent to the seal plate 82 at a portion where the recess 74 is formed in the direction of the rotation axis CL. The seal plate 84 is disposed in the entire area facing the intermediate shaft cover upper half 60 in the radial direction. The end portion on the intermediate shaft cover upper half 60 side of the seal plate 84 is in contact with the intermediate shaft cover upper half 60 and seals between the intermediate shaft cover upper half 60 and the intermediate shaft cover lower half 62.

  As described above, the stationary blade support mechanism 50 has a fan-shaped support ring upper half 64 that is larger than a semicircle in the circumferential direction, that is, larger than 180 °. In addition, a relief portion 70 is formed at the circumferential end of the support ring upper half 64. Further, a flange portion 72 and a recess 73 are formed in the support ring upper half 64 and the support ring lower half 66, and a flange portion 71 and a recess 74 are formed in the intermediate shaft cover upper half 60 and the intermediate shaft cover lower half 62. .

By forming the relief portion 70, the stationary blade support mechanism 50 has an outer peripheral surface of the intermediate shaft cover lower half 62 on the arc and an inner peripheral surface of the relief portion 70 of the support ring upper half 64 as shown in FIG. A space A ₁ and a space A ₂ are formed between the _two . At this time, the stationary blade support mechanism 50 forms the flange portion 71, the flange portion 72, the concave portion 73, and the concave portion 74, so that the space A ₁ and the space A ₂ are shifted from each other when viewed from the rotation axis CL direction. Can not be formed). Further, since the support ring side end surface 77 and the intermediate shaft cover side end surface 79 corresponding to the relief portion 70 come into contact with each other, it is difficult for air to leak from between the support ring side end surface 77 and the intermediate shaft cover side end surface 79.

Thus, the stator blade support mechanism 50 is offset space A ₁ and the space A ₂ (non-overlapping) by forming a position, it is possible to reduce the area where the space A ₁ and the space A ₂ are connected. Here, the stationary blade support mechanism 50, the space A ₁ than vane support mechanism 50 is connected to the atmosphere in the flow direction upstream side of the combustion gas G, the combustion gas than space A ₂ are vane support mechanism 50 G It is connected to the atmosphere on the downstream side of the flow direction. For this reason, even if the stationary blade support mechanism 50 has a structure in which a space is formed when the relief portion 76 is formed, the air passing through the relief portion 76 can be reduced. Specifically, it is possible only to the portion of the gap between the support ring top half 64 and support ring lower half 66 that are connected to the space A _1.

Furthermore, in this embodiment, by providing the seal plate 82, the gap between the support ring upper half 64 and the support ring lower half 66 can be closed. Stationary blade support mechanism 50, by providing the sealing plate 82, as shown in FIG. 10, in particular FIGS. 8 to 10, between the space A ₁ and the space A ₂ are, support ring upper half 64 and the ring under half Of the clearances 66, only the space A ₃ surrounded by the seal plate 82, the support ring upper half 64, the support ring lower half 66, and the intermediate shaft cover lower half 62 can be connected. That even if the relief portion is formed, a space in which the upstream and downstream sides of the fuel gas via a stationary blade support mechanism 50 is connected may be only space A _3. Thereby, the fluid which moves to the downstream side of the fuel gas via the stationary blade support mechanism 50 can be reduced.

  Even if the support ring upper half 64 and the support ring lower half 66 of the support ring 54 do not form a semicircle, the stationary blade support mechanism 50 makes the support ring upper half 64 larger than the semicircle as in the present embodiment, for example. However, it can be easily installed by providing a relief portion. Furthermore, the stationary blade support mechanism 50 is provided with the flange portion 71 or the flange portion 72, that is, provided with a step in the radial direction, forms a protruding space, and closes the space formed due to the shape of the relief portion 70. Thus, it is possible to divide the space formed by the relief portion and to prevent the fluid from flowing through the relief portion 70.

  Thereby, the stationary blade support mechanism 50 can suppress the fluid from leaking from the divided position while dividing the annular member at an arbitrary position other than the semicircular portion. Thereby, the efficiency of operation can be maintained while increasing the degree of freedom of design. For example, when an odd number of turbine stationary blade bodies 27 are arranged in the circumferential direction and the support ring is divided between the turbine stationary blade body 27 and the turbine stationary blade body 27, the position cannot be a semicircle. However, in this case as well, the support ring is divided between the turbine stationary blade body 27 and the turbine stationary blade body 27, and air leakage at the divided positions can be suppressed.

Here, the sealing plate 82 is preferably disposed in the space A ₁ side formed by the relief portion 76 of the center of the rotation axis direction of the end face. Specifically, as shown in FIG. 7, the distance d _{1 in} the rotation axis direction from the support ring side end surface 77 to the seal plate 82 is preferably less than half of the distance d _{2 in} the rotation axis direction of the flange portion 72. . Thus, it is possible to further reduce the space A _3, can be suppressed leakage of air.

FIG. 11 is a top view showing the vicinity of the end face of the lower member of the modified stationary blade support mechanism. Further, the stationary blade support mechanism 50, as shown in FIG. 11, it is preferable to provide an auxiliary seal plate 92 for closing the space A _3. The auxiliary seal plate 92 is a plate that protrudes toward the support ring upper half 64 of the lower support ring half 66, and extends in the direction of the rotation axis CL. The auxiliary seal plate 92 is disposed at a position surrounded by the seal plate 82, the support ring upper half 64, the support ring lower half 66, and the intermediate shaft cover lower half 62. Auxiliary seal plate 92, closing the space A3 surrounded by the sealing plate 82 and the support ring upper half 64 and support ring lower half 66 and the intermediate shaft cover the lower half 62, specifically, the space A ₁ space A ₃ it is preferable to divide into a side of the space and the space a ₂ side space. Thus, it is possible to suppress the fluid moves into the space A ₂ from the space A ₁ through the space A _3. The auxiliary sealing plates 92, by closing the part of the space A _3, it is possible to easily flow the fluid is not limited to be arranged in the entire area.

  In the above embodiment, the support ring 54 is provided with a flange portion that is a convex portion, but the present invention is not limited to this. FIG. 12 is a top view showing the vicinity of the end face of the lower member of the stationary blade support mechanism of another embodiment. The stator blade support mechanism 50a shown in FIG. 12 is provided with a concave portion 172 that is recessed radially outward in the lower ring half 66a of the support ring, and a flange portion that protrudes radially outward in the intermediate shaft cover lower half 62a of the intermediate bearing. 174 is provided. The bearing upper half and the ring upper half have the same structure. Thus, even if the position where the flange portion 174 is provided is reversed, the space can be closed in the same manner as in the above embodiment, and air leakage can be suppressed.

  Further, the relief portion only needs to be accessible from the divided support ring radial direction without being interfered with the intermediate bearing and the support ring at the time of assembling or the like. The stationary blade support mechanism may be provided with a relief portion in the intermediate bearing. FIG. 13: is a front view which shows the vicinity of the contact part of the upper member and lower member of the stationary blade support mechanism of another Example. The stationary blade support mechanism 50b shown in FIG. 13 includes an intermediate bearing including an intermediate shaft cover upper half 60b, an intermediate shaft cover lower half 62b, a support ring including a support ring upper half 64b, and a ring lower half 66b. Have FIG. 13 shows only one of the dividing surfaces, but the other has the same structure.

  The intermediate shaft cover upper half 60b has a relief portion 220 in the vicinity of the end surface that contacts the intermediate shaft cover lower half 62b. The relief portion 220 has a shape in which a portion whose width in a direction orthogonal to the direction in which the support ring upper half 64b is inserted (horizontal direction in this embodiment) is wider than the distance connecting both ends of the support ring upper half 64b is cut. It becomes. In other words, a part of the outer peripheral surface of the arc is cut off.

  The intermediate shaft cover lower half 62b has a relief portion 222 in the vicinity of the end surface that contacts the bearing upper half 60b. Similar to the relief portion 220, the relief portion 222 is wider in the direction orthogonal to the direction in which the support ring upper half 64b is inserted (in the horizontal direction in this embodiment) than the distance connecting both ends of the support ring upper half 64b. The part which becomes becomes the shape where it was shaved. In other words, a part of the outer peripheral surface of the arc is cut off. Further, in the stationary blade support mechanism 50b, a flange portion 271 is formed on the support ring upper half 64b, and a flange portion 272 is formed on the lower ring half 66b.

  As described above, even when the relief portions 220 and 222 are provided in the intermediate bearing, the above-described effects can be obtained by providing the flange portions and the corresponding concave portions and dividing the spaces generated by the relief portions 220 and 222.

  Moreover, in the said Example, although the flange part was provided as a structure which block | closes the space formed in a relief part, it is not limited to a flange part. For example, a plate-like protruding portion that closes a space formed by the relief portion when viewed from the rotation direction and a corresponding concave portion may be provided in the vicinity of the relief portion.

  Moreover, in the said Example, although the support ring upper half of the support ring which is an outer periphery ring was larger than the semicircle in the circumferential direction, ie, larger than 180 degrees, it was not limited to this. For example, even if the upper half of the support ring that is the outer ring is a semicircle in the circumferential direction, by providing a relief part, the upper half of the support ring is in the middle with the end face of the upper half of the support ring inclined relative to the horizontal direction. Can be attached to the shaft cover. That is, even when the upper half of the support ring is attached to the intermediate shaft cover in a direction inclined in the horizontal direction, the upper half of the support ring can be attached from the upper side in the vertical direction. Thereby, it can be made easy to assemble.

  Moreover, in the said Example, although demonstrated as a structure of the stationary blade support mechanism of the gas turbine 10, it can apply also other than a stationary blade support mechanism. This structure can be used for various applications as a stationary member of a rotating machine. The stationary member may have a structure including an inner peripheral ring corresponding to the intermediate bearing and an outer peripheral ring corresponding to the support ring.

DESCRIPTION OF SYMBOLS 10 Gas turbine 11 Compressor 12 Combustor 13 Turbine 14 Generator 21 Air intake 22 Compressor compartment 23 Compressor vane body 24 Compressor blade body 25 Extraction chamber (low pressure gas supply source)
26 Turbine casing 27 Turbine stator blade body 28 Turbine rotor blade body 32 Rotor 41 Stator blade (turbine stator blade)
42 Rotor blade (turbine rotor blade)
43 outer shroud 44 inner shroud 46 rotor disk 50, 50a, 50b stationary blade support mechanism (stationary member of rotating body)
52 Intermediate shaft cover 54 Support ring 56 Fastening portion 60, 60b Intermediate shaft cover upper half 62, 62a, 62b Intermediate shaft cover lower half 64, 64a, 64b Support ring upper half 66, 66b Support ring lower half 70, 76 Relief portion 71 72 Flange (blocking part)
73 and 74 the recess 77 the support ring side end surface 79 the intermediate shaft cover side end surfaces 82 sealing plate 92 auxiliary seal plate 100 horizontal 102 divided surface 172 recess 174 flange portion 220, 222 the relief portion 271, 272 the flange portion A _1, A ₂ , A ₃ space CL rotation axis

Claims (10)

A stationary member of a rotating machine,
A peripheral ring in which a plurality of partial peripheral rings divided into a ring shape are connected;
An inner ring that is inscribed in the outer ring,
In the outer ring, one of the partial outer rings is a main partial outer ring,
At least one of the circumferential end of the main part outer ring or the part of the inner ring facing the circumferential end of the main part outer ring is the circumferential end of the main part outer ring. A relief part having a shape other than an arc is formed so as to be larger in the radial direction than the outer peripheral surface of the inner ring,
At least a portion of the portion where the relief portion is formed is formed on an end surface in the axial direction of the rotating machine and faces the end portion of the main portion outer ring or the end portion of the main portion outer ring of the inner ring. On the other hand, when viewed from the rotation axis direction of the rotating machine, a blocking portion is formed that covers the entire space between the main portion outer peripheral ring and the inner peripheral ring formed in the relief portion. A stationary member of a rotating machine.   The stationary member for a rotary machine according to claim 1, wherein the main part outer peripheral ring is an arc larger than a half circumference.   3. The stationary member for a rotary machine according to claim 1, wherein the relief portion is formed on the outer circumferential ring of the main portion, and extends in a tangential direction of the arc from an end portion of a semicircular arc.   The stationary member for a rotary machine according to any one of claims 1 to 3, wherein the main part outer peripheral ring is disposed in a portion including an end portion on a vertical upper side of the outer peripheral ring.   The said closing part is formed in the said inner periphery ring, The flange part which protruded in the said outer periphery ring side rather than the part in which the said relief part is formed is included, The any one of Claim 1 to 3 characterized by the above-mentioned. A stationary member of the rotating machine according to 1.   The said closed part is formed in the said main part outer periphery ring, The flange part which protruded in the said inner peripheral ring side rather than the part in which the said relief part is formed is included, The any one of Claim 1 to 4 characterized by the above-mentioned. A stationary member of a rotating machine according to one item.   The outer circumferential ring and the inner circumferential ring are formed on one of a circumferential end surface of the closing portion or a surface facing the circumferential end surface of the closing portion, and in a radial direction, over the entire region overlapping the relief portion. 7. The seal plate according to claim 1, further comprising a seal plate that extends and contacts a circumferential end surface of the closing portion or a surface facing the circumferential end surface of the closing portion. Stationary member of a rotating machine.   The stationary member for a rotary machine according to claim 7, wherein the seal plate is disposed closer to a space formed by the relief portion than an axial center of the end surface.   The stationary member for a rotary machine according to claim 7 or 8, wherein the seal plate is formed on a surface facing an end surface in a circumferential direction of the closing portion. A compressor for compressing the taken-in air;
A combustor for supplying and burning fuel to compressed air compressed by the compressor;
A turbine that obtains rotational power from the combustion gas burned in the combustor,
The turbine is a stationary member of a rotating machine according to any one of claims 1 to 9,
A gas turbine comprising: a plurality of stationary blades supported on an outer periphery of an outer peripheral ring of a stationary member of the rotating machine.

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